Combustion control method, device and equipment of gas turbine and storage medium

Abstract

The invention relates to the technical field of gas turbines, in particular to a combustion control method, device and equipment of a gas turbine and a storage medium. Current working parameters of the gas turbine are obtained, and the to-be-adjusted working parameters of the gas turbine and the adjustment priority among the to-be-adjusted working parameters are judged according to the current working parameters; and finally, the operation state of the gas turbine is adjusted based on the adjustment priority and the to-be-adjusted working parameters, so that the to-be-adjusted working parameters of the gas turbine are reduced to be within a preset safe working parameter interval, the combustion process of the gas turbine is interfered, the combustion performance of the gas turbine is improved, and the safety of the gas turbine is improved. The technical problem that in the prior art, the combustion performance of a gas turbine fluctuates, and consequently the pollutant emission amount of the gas turbine is too high is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a combustion control method, device, equipment and storage medium for a gas turbine. Background Art

[0002] During the operation of the gas turbine, the combustion performance of the gas turbine may be reduced due to external environment, changes in fuel composition or structural blockage, resulting in a large amount of pollutant emissions, violating local environmental protection standards. At the same time, the combustion performance of the gas turbine under different loads will also affect the combustion stability in the combustion chamber. More seriously, it will cause the gas turbine to malfunction and reduce the working efficiency of the gas turbine.

[0003] The above contents are only used to assist in understanding the technical solution of the present invention and do not constitute an admission that the above contents are prior art. Summary of the invention

[0004] The main purpose of the present invention is to provide a combustion control method, device, equipment and storage medium for a gas turbine, aiming to solve the technical problem in the prior art that the combustion performance of the gas turbine fluctuates, resulting in excessive pollutant emissions from the gas turbine.

[0005] To achieve the above object, the present invention provides a combustion control method for a gas turbine, the method comprising the following steps:

[0006] Obtain current operating parameters of the gas turbine;

[0007] Determining the working parameter to be adjusted and the adjustment priority between the working parameters to be adjusted according to the current working parameter;

[0008] The operating state of the gas turbine is adjusted based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0009] Optionally, the adjusting the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range includes:

[0010] generating a target adjustment order of each working parameter to be adjusted based on the adjustment priority and the working parameter to be adjusted;

[0011] The operating state of the gas turbine is adjusted according to the target adjustment sequence and the target fuel adjustment strategy corresponding to each operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0012] Optionally, the operating parameters to be adjusted include: NOx exhaust concentration, CO exhaust concentration and combustion chamber pressure pulsation parameters of the gas turbine in various frequency bands;

[0013] The operating state of the gas turbine is adjusted according to the target fuel adjustment strategy corresponding to each operating parameter to be adjusted, including:

[0014] When the operating parameter to be adjusted is NOx exhaust concentration, at least one of the following steps is performed:

[0015] controlling the gas turbine to perform flue gas circulation;

[0016] Increasing the valve opening corresponding to the air in the gas turbine;

[0017] The combustion temperature of each zone of the combustion chamber in the gas turbine is controlled.

[0018] Optionally, the combustion control method of the gas turbine further includes:

[0019] When the working parameter to be adjusted is CO exhaust concentration, at least one of the following steps is performed:

[0020] Open the premixing chamber so that the fuel and air are mixed in the premixing chamber before entering the combustion chamber;

[0021] adjusting the pressure pulsation parameters of the combustion chamber;

[0022] The valve opening of at least one fuel inlet communicating with the combustion chamber is controlled to control the fuel flow rate.

[0023] Optionally, the combustion control method of the gas turbine further includes:

[0024] When the working parameter to be adjusted is a combustion chamber pressure pulsation parameter, continuously acquiring the pressure pulsation parameter in the combustion chamber;

[0025] Performing data analysis on the pressure pulsation parameters to determine the load state of the combustion chamber;

[0026] A valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted based on the load state.

[0027] Optionally, adjusting the valve opening of at least one fuel inlet communicating with the combustion chamber based on the load state comprises:

[0028] When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber;

[0029] When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

[0030] Optionally, the priorities of the pressure pulsation parameter, the NOx exhaust concentration and the CO exhaust concentration are sequentially reduced.

[0031] In addition, to achieve the above-mentioned object, the present invention further provides a combustion control device for a gas turbine, the combustion control device for a gas turbine comprising:

[0032] An acquisition module, used for acquiring current operating parameters of the gas turbine;

[0033] A determination module, used to determine the working parameter to be adjusted and the adjustment priority between the working parameters to be adjusted according to the current working parameter;

[0034] An adjustment module is used to adjust the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0035] In addition, to achieve the above-mentioned purpose, the present invention also proposes a combustion control device of a gas turbine, wherein the combustion control device of the gas turbine comprises: a memory, a processor, and a combustion control program of the gas turbine stored in the memory and executable on the processor, wherein the combustion control program of the gas turbine is configured to implement the steps of the combustion control method of the gas turbine as described above.

[0036] In addition, to achieve the above-mentioned purpose, the present invention also proposes a storage medium, on which a combustion control program of a gas turbine is stored. When the combustion control program of the gas turbine is executed by a processor, the steps of the combustion control method of the gas turbine as described above are implemented.

[0037] In addition, to achieve the above-mentioned purpose, the present application also provides a computer program product, which includes a computer program, and when the computer program is executed by a processor, the steps of the combustion control method of the gas turbine as described above are implemented.

[0038] One or more technical solutions proposed in the present invention have at least the following technical effects: a combustion control method for a gas turbine, the combustion control method for the gas turbine comprising: obtaining current operating parameters of the gas turbine; determining the adjustment priority between the operating parameters to be adjusted and each operating parameter to be adjusted according to the current operating parameters; adjusting the operating state of the gas turbine based on the adjustment priority and the operating parameters to be adjusted until the operating parameters to be adjusted are reduced to within a preset safe operating parameter range. Compared with the prior art, the present invention obtains the current operating parameters of the gas turbine, and determines the operating parameters to be adjusted of the gas turbine and the adjustment priority between each operating parameter to be adjusted according to the current operating parameters, and finally adjusts the operating state of the gas turbine based on the adjustment priority and the operating parameters to be adjusted, so that the operating parameters to be adjusted of the gas turbine are reduced to within the preset safe operating parameter range, thereby interfering with the combustion process of the gas turbine, improving the combustion performance of the gas turbine, and avoiding the technical problem in the prior art that the combustion performance of the gas turbine fluctuates and the pollutant emissions of the gas turbine are too high. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0040] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0041] Figure 1 It is a flow chart of a first embodiment of a combustion control method for a gas turbine according to the present invention;

[0042] Figure 2 It is a flow chart of a second embodiment of a combustion control method for a gas turbine according to the present invention;

[0043] Figure 3 It is a structural block diagram of a first embodiment of a combustion control device for a gas turbine according to the present invention;

[0044] Figure 4 It is a structural schematic diagram of a combustion control device of a gas turbine in a hardware operating environment involved in an embodiment of the present invention.

[0045] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0046] It should be understood that the specific embodiments described herein are only used to explain the technical solutions of the present application and are not used to limit the present application.

[0047] In order to better understand the technical solution of the present application, a detailed description will be given below in conjunction with the accompanying drawings and specific implementation methods.

[0048] Based on this, an embodiment of the present invention provides a combustion control method for a gas turbine, referring to Figure 1 , Figure 1 The figure is a flow chart of a first embodiment of a combustion control method for a gas turbine according to the present invention.

[0049] In this embodiment, the combustion control method of the gas turbine includes:

[0050] Step S10: Acquire the current operating parameters of the gas turbine.

[0051] It should be noted that the execution subject of this embodiment may be a computing service device with data processing, network communication and program running functions, such as a tablet computer, a personal computer, a mobile phone, etc., or an electronic device capable of realizing the above functions, a control computer electrically connected to a gas turbine, etc. The following takes a control computer electrically connected to a gas turbine as an example to illustrate this embodiment and the following embodiments.

[0052] In this embodiment, the current operating parameters of the gas turbine include but are not limited to the gas emissions and combustion chamber pressure pulsation of the gas turbine during operation, wherein the gas emissions include but are not limited to various NOx gases and CO, etc. A large amount of polluting gases will be emitted during the operation of the gas turbine. Excessive polluting gases will cause environmental pollution, and incomplete combustion will occur. The combustion residue will subsequently affect the service life of the equipment, and the combustion chamber pressure pulsation data will affect the normal operation of the gas turbine. Too low combustion chamber pressure may cause the gas turbine to stall, and frequent shutdown and restart will seriously damage the service life of the equipment.

[0053] Furthermore, after obtaining the current operating parameters of the gas turbine, the method further includes:

[0054] The current working parameters are preprocessed, and the preprocessing at least includes: moving arithmetic average, exponentially weighted moving average and extreme value processing.

[0055] Since it is difficult to collect the working parameters of the gas turbine during operation, especially the emission of pollutant gases, it is difficult to directly use it for subsequent combustion adjustment judgment and single adjustment step calculation. For example, when obtaining the pressure pulsation data of the combustion chamber, a combustion chamber pressure probe or a high-speed pressure sensor and other devices can be used for collection. In order to improve the accuracy of the combustion chamber pressure pulsation data, the arithmetic average of multiple collected pressure pulsation data can be performed to improve the accuracy of the pressure pulsation data within a time period. When collecting the emission of pollutant gases, a continuous emission monitoring system (CEMS) can be used to monitor and record the concentration and emission of industrial pollutants in real time, or a risk evaluation and mitigation strategy system (REMS). Other devices or equipment that can realize gas emission collection can also be used. This embodiment does not impose specific restrictions on this.

[0056] Step S20: determining the operating parameter to be adjusted and the adjustment priority among the operating parameters to be adjusted according to the current operating parameter.

[0057] The working parameters to be adjusted refer to working parameters that partially exceed the corresponding preset safe working parameter range. When determining the working parameters to be adjusted, they can be determined by comparing the range in which the current working parameters are located. Different gas turbines and current environmental emission standards will also directly affect the range of the corresponding preset safe working parameter range. A priority will be pre-set between different working parameters. In this embodiment, the priorities of pressure pulsation parameters, NOx exhaust concentration and CO exhaust concentration decrease in sequence.

[0058] For example: the local environmental protection standard requires that the NOx exhaust concentration shall not be greater than 35mg / m3. Then, when the NOx exhaust concentration of the gas turbine is 36mg / m3, the NOx exhaust concentration is the working parameter to be adjusted. If the working parameter to be adjusted is only the NOx exhaust concentration, it is only necessary to adjust the operating state of the gas turbine to reduce the NOx exhaust concentration of the gas turbine to below 35mg / m3. If the working parameters to be adjusted are the NOx exhaust concentration and the pressure pulsation parameter, it is necessary to adjust the pressure pulsation parameter first, and then adjust the NOx exhaust concentration to the corresponding preset safe working parameter range.

[0059] Step S30: adjusting the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0060] It should be noted that the control of the gas turbine in this embodiment is different for different operating parameters to be adjusted, because in different environments, adjusting a certain operating parameter of the gas turbine may cause changes in another operating parameter. For example, flue gas circulation technology can be used to reduce the generation of NOx, but it may lead to increased CO emissions and poor low-load stability.

[0061] This embodiment obtains the current operating parameters of the gas turbine, and determines the operating parameters to be adjusted of the gas turbine and the adjustment priorities among the operating parameters to be adjusted through the current operating parameters, and finally adjusts the operating state of the gas turbine based on the adjustment priorities and the operating parameters to be adjusted, so that the operating parameters to be adjusted of the gas turbine are reduced to within a preset safe operating parameter range, thereby interfering with the combustion process of the gas turbine, improving the combustion performance of the gas turbine, and avoiding the technical problem in the prior art that the combustion performance of the gas turbine fluctuates, resulting in excessive pollutant emissions from the gas turbine.

[0062] Based on the first embodiment of the present application, in the second embodiment of the present application, the same or similar contents as those in the above-mentioned embodiment 1 can be referred to the above introduction, and will not be repeated in the following. Figure 2 , step S30, comprising:

[0063] Step S301: generating a target adjustment sequence of each working parameter to be adjusted based on the adjustment priority and the working parameter to be adjusted.

[0064] Step S302: adjusting the operating state of the gas turbine according to the target adjustment sequence and the target fuel adjustment strategy corresponding to each operating parameter to be adjusted, until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0065] It should be noted that, in this embodiment, the higher the adjustment priority, the earlier the adjustment order, among which the priorities of pressure pulsation parameters, NOx exhaust concentration and CO exhaust concentration decrease in turn, then the adjustment order of the working parameters to be adjusted is pressure pulsation parameters, NOx exhaust concentration and CO exhaust concentration.

[0066] The pressure pulsation parameters, NOx exhaust concentration and CO exhaust concentration are all related to the combustion performance of the combustion chamber in the gas turbine. Generally speaking, the more complete the combustion, the lower the NOx exhaust concentration and CO exhaust concentration. Secondly, it is also related to the composition of the fuel, but the fuel composition will not be changed in this embodiment. The pressure pulse parameter is related to the load state of the combustion chamber. The pressure pulsation parameter cannot be too high or too low, and it is best to be in a suitable pressure range. Too high a pressure pulsation parameter will reduce the service life of the equipment, and too low a pressure pulse parameter may cause the gas turbine to shut down and incomplete combustion, resulting in the generation of a large amount of polluting gas.

[0067] When different technologies are used to interfere with the combustion conditions in the combustion chamber, the degree of influence on the pressure pulsation parameters, NOx exhaust concentration and CO exhaust concentration varies. Therefore, different adjustment technologies can be used when adjusting different working parameters in this embodiment.

[0068] Furthermore, the operating state of the gas turbine is adjusted according to the target fuel adjustment strategy corresponding to each operating parameter to be adjusted, including:

[0069] When the operating parameter to be adjusted is NOx exhaust concentration, at least one of the following steps is performed:

[0070] controlling the gas turbine to perform flue gas circulation;

[0071] Increasing the valve opening corresponding to the air in the gas turbine;

[0072] The combustion temperature of each zone of the combustion chamber in the gas turbine is controlled.

[0073] It should be noted that for traditional composite fuels, flue gas circulation refers to recycling part of the flue gas to the combustion chamber to reduce the oxygen concentration in the combustion chamber, thereby reducing the generation of NOx and significantly reducing NOx emissions, but may lead to increased CO emissions and poor low-load stability. Increasing the valve opening corresponding to the air in the gas turbine, for certain low calorific value fuels and hydrogen fuels, can increase the oxygen content in the combustion chamber and reduce the participation of nitrogen, thereby reducing NOx emissions. However, the gas turbine needs to be equipped with an air separation device, otherwise it will simultaneously lead to the participation of nitrogen in the air, which may reduce the system efficiency.

[0074] Controlling the combustion temperature of each area of ​​the combustion chamber in the gas turbine can reduce the generation of thermal NOx. For example, the combustion temperature and residence time can be controlled by homogeneous premixing of lean fuel to achieve the purpose of reducing NOx emissions.

[0075] Furthermore, the combustion control method of the gas turbine further includes:

[0076] When the working parameter to be adjusted is CO exhaust concentration, at least one of the following steps is performed:

[0077] Open the premixing chamber so that the fuel and air are mixed in the premixing chamber before entering the combustion chamber;

[0078] adjusting the pressure pulsation parameters of the combustion chamber;

[0079] The valve opening of at least one fuel inlet communicating with the combustion chamber is controlled to control the fuel flow rate.

[0080] It can be understood that when adjusting the CO exhaust concentration, for a gas turbine with a premixing chamber, the fuel and air can be mixed in the premixing chamber before entering the combustion chamber to ensure sufficient mixing of the fuel and air to promote more complete combustion, thereby reducing the generation of CO. In addition, supercharged combustion can be achieved through high-frequency or continuous detonation waves to improve the cycle efficiency. In addition, the flow rate of the fuel involved in the combustion can be adjusted to control the fuel content in the combustion chamber, thereby controlling the combustion chamber to be in a suitable combustion condition and reducing the CO exhaust concentration.

[0081] Furthermore, the combustion control method of the gas turbine further includes:

[0082] When the working parameter to be adjusted is a combustion chamber pressure pulsation parameter, continuously acquiring the pressure pulsation parameter in the combustion chamber;

[0083] Performing data analysis on the pressure pulsation parameters to determine the load state of the combustion chamber;

[0084] A valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted based on the load state.

[0085] It should be understood that data analysis of pressure pulsation parameters can be performed by using spectrum analysis methods such as fast Fourier transform (FFT) to convert time domain signals into frequency domain in order to identify pressure pulsation characteristics at specific frequencies, and then decompose the original signal into several intrinsic mode functions (IMFs) to more accurately extract the characteristics of the original signal. The trained thermodynamic model is used to simulate the combustion behavior under different working conditions and predict the changes in pressure pulsation. Then, by adjusting the valve opening of at least one fuel inlet connected to the combustion chamber, the changing trend of the pressure pulsation parameters of the combustion chamber in the next cycle is predicted, so that intervention can be carried out in advance.

[0086] Further, adjusting the valve opening of at least one fuel inlet connected to the combustion chamber based on the load state includes:

[0087] When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber;

[0088] When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

[0089] Specifically, if the combustion chamber is in a high-load state, the fuel flow rate entering the combustion chamber can be reduced, thereby reducing the fuel content in the combustion chamber, avoiding incomplete combustion, and reducing the fuel load in the combustion chamber at the same time; if the combustion chamber is in a low-load state, the fuel flow rate in the combustion chamber can be increased, that is, the combustion efficiency of the combustion chamber can be increased, and the gas turbine can be prevented from shutting down due to insufficient combustion performance in a low-pressure environment.

[0090] This embodiment generates a target adjustment order for each working parameter to be adjusted based on the adjustment priority and the working parameter to be adjusted; adjusts the operating state of the gas turbine according to the target adjustment order and the target fuel adjustment strategy corresponding to each working parameter to be adjusted until the working parameter to be adjusted is reduced to within a preset safe working parameter range, and minimizes the deviation of each working parameter to be adjusted from the corresponding preset safe working parameter range by setting corresponding adjustment orders for different working parameters.

[0091] The present application also provides a combustion control device for a gas turbine, please refer to Figure 3 , the combustion control device of the gas turbine comprises:

[0092] The acquisition module 10 is used to acquire the current operating parameters of the gas turbine.

[0093] The determination module 20 is used to determine the working parameter to be adjusted and the adjustment priority among the working parameters to be adjusted according to the current working parameter.

[0094] The adjustment module 30 is used to adjust the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

[0095] This embodiment obtains the current operating parameters of the gas turbine, and determines the operating parameters to be adjusted of the gas turbine and the adjustment priorities among the operating parameters to be adjusted through the current operating parameters, and finally adjusts the operating state of the gas turbine based on the adjustment priorities and the operating parameters to be adjusted, so that the operating parameters to be adjusted of the gas turbine are reduced to within a preset safe operating parameter range, thereby interfering with the combustion process of the gas turbine, improving the combustion performance of the gas turbine, and avoiding the technical problem in the prior art that the combustion performance of the gas turbine fluctuates, resulting in excessive pollutant emissions from the gas turbine.

[0096] In one embodiment, the adjustment module 30 is also used to generate a target adjustment order for each working parameter to be adjusted based on the adjustment priority and the working parameter to be adjusted; and adjust the operating state of the gas turbine according to the target adjustment order and the target fuel adjustment strategy corresponding to each working parameter to be adjusted until the working parameter to be adjusted is reduced to within a preset safe working parameter range.

[0097] In one embodiment, the adjustment module 30 is also used to perform at least one of the following steps when the working parameter to be adjusted is the NOx exhaust concentration: controlling the gas turbine to perform flue gas circulation; increasing the valve opening corresponding to the air in the gas turbine; and controlling the combustion temperature of each area of ​​the combustion chamber in the gas turbine.

[0098] In one embodiment, the adjustment module 30 is further used to perform at least one of the following steps when the working parameter to be adjusted is the CO exhaust concentration: open the premixing chamber to allow the fuel and air to mix in the premixing chamber before entering the combustion chamber; adjust the pressure pulsation parameters of the combustion chamber; control the valve opening of at least one fuel inlet connected to the combustion chamber to control the fuel flow rate.

[0099] In one embodiment, the adjustment module 30 is also used to continuously obtain the pressure pulsation parameters in the combustion chamber when the working parameter to be adjusted is the pressure pulsation parameter of the combustion chamber; perform data analysis on the pressure pulsation parameters to determine the load state of the combustion chamber; and adjust the valve opening of at least one fuel inlet connected to the combustion chamber based on the load state.

[0100] In one embodiment, the adjustment module 30 is further used to reduce the valve opening of at least one fuel inlet connected to the combustion chamber when the load state is a high load state; and to increase the valve opening of at least one fuel inlet connected to the combustion chamber when the load state is a low load state.

[0101] In one embodiment, the adjustment module 30 is further configured to sequentially reduce the priorities of the pressure pulsation parameter, the NOx exhaust concentration, and the CO exhaust concentration.

[0102] The present application provides a combustion control device for a gas turbine, the combustion control device for a gas turbine comprising: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor so that the at least one processor can execute the combustion control method for the gas turbine in the above-mentioned embodiment one.

[0103] Reference below Figure 4, which shows a schematic diagram of the structure of a combustion control device for a gas turbine suitable for implementing an embodiment of the present application. The combustion control device for a gas turbine in the embodiment of the present application may include, but is not limited to, mobile terminals such as mobile phones, laptop computers, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Portable Application Descriptions), PMPs (Portable Media Players), vehicle-mounted terminals (such as vehicle-mounted navigation terminals), etc., and fixed terminals such as digital TVs, desktop computers, etc. Figure 4 The combustion control device of the gas turbine shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0104] like Figure 4 As shown, the combustion control device of the gas turbine may include a processing device 1001 (e.g., a central processing unit, a graphics processing unit, etc.), which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM: Read Only Memory) 1002 or a program loaded from a storage device 1003 to a random access memory (RAM: Random Access Memory) 1004. Various programs and data required for the operation of the combustion control device of the gas turbine are also stored in the RAM 1004. The processing device 1001, the ROM 1002, and the RAM 1004 are connected to each other via a bus 1005. An input / output (I / O) interface 1006 is also connected to the bus. Typically, the following systems may be connected to the I / O interface 1006: input devices 1007 including, for example, a touch screen, a touchpad, a keyboard, a mouse, an image sensor, a microphone, an accelerometer, a gyroscope, etc.; output devices 1008 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; storage devices 1003 including, for example, a magnetic tape, a hard disk, etc.; and communication devices 1009. The communication device 1009 may allow the combustion control device of the gas turbine to communicate with other devices wirelessly or by wire to exchange data. Although the combustion control device of the gas turbine having various systems is shown in the figure, it should be understood that it is not required to implement or have all the systems shown. More or fewer systems may be implemented or have instead.

[0105] In particular, according to the embodiments disclosed in the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiments disclosed in the present application include a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from a network through a communication device, or installed from a storage device 1003, or installed from a ROM 1002. When the computer program is executed by the processing device 1001, the above-mentioned functions defined in the method of the embodiment disclosed in the present application are executed.

[0106] The combustion control device of the gas turbine provided by the present application adopts the combustion control method of the gas turbine in the above embodiment, which can solve the technical problem of combustion control of the gas turbine. Compared with the prior art, the beneficial effects of the combustion control device of the gas turbine provided by the present application are the same as the beneficial effects of the combustion control method of the gas turbine provided by the above embodiment, and other technical features in the combustion control device of the gas turbine are the same as the features disclosed in the method of the previous embodiment, which will not be repeated here.

[0107] It should be understood that the various parts disclosed in this application can be implemented by hardware, software, firmware or a combination thereof. In the description of the above embodiments, specific features, structures, materials or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0108] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

[0109] The present application provides a computer-readable storage medium having computer-readable program instructions (ie, computer programs) stored thereon, and the computer-readable program instructions are used to execute the combustion control method of the gas turbine in the above-mentioned embodiment.

[0110] The computer-readable storage medium provided in the present application may be, for example, a USB flash drive, but is not limited to electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, systems or devices, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In this embodiment, the computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, system or device. The program code contained on the computer-readable storage medium may be transmitted using any appropriate medium, including but not limited to: wires, optical cables, RF (Radio Frequency), etc., or any suitable combination of the above.

[0111] The computer-readable storage medium may be included in the combustion control device of the gas turbine; or may exist independently without being assembled into the combustion control device of the gas turbine.

[0112] The computer-readable storage medium carries one or more programs. When the one or more programs are executed by the combustion control device of the gas turbine, the combustion control device of the gas turbine performs combustion control of the gas turbine.

[0113] Computer program code for performing the operations of the present application may be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0114] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0115] The modules involved in the embodiments described in this application may be implemented by software or hardware, wherein the name of the module does not constitute a limitation on the unit itself in some cases.

[0116] The readable storage medium provided in the present application is a computer-readable storage medium, which stores computer-readable program instructions (i.e., computer programs) for executing the above-mentioned combustion control method of the gas turbine, and can solve the technical problem of combustion control of the gas turbine. Compared with the prior art, the beneficial effects of the computer-readable storage medium provided in the present application are the same as the beneficial effects of the combustion control method of the gas turbine provided in the above-mentioned embodiment, and will not be repeated here.

[0117] The present application also provides a computer program product, comprising a computer program, wherein when the computer program is executed by a processor, the steps of the combustion control method of the gas turbine as described above are implemented.

[0118] The computer program product provided in this application can solve the technical problem of combustion control of gas turbines. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as the beneficial effects of the combustion control method of the gas turbine provided in the above embodiment, which will not be repeated here.

[0119] The above descriptions are only some embodiments of the present application, and are not intended to limit the patent scope of the present application. All equivalent structural changes made using the contents of the present application specification and drawings under the technical concept of the present application, or direct / indirect applications in other related technical fields are included in the patent protection scope of the present application.

Claims

1. A combustion control method for a gas turbine, characterized in that: The combustion control method of the gas turbine comprises: Obtain current operating parameters of the gas turbine; Determining the working parameter to be adjusted and the adjustment priority between the working parameters to be adjusted according to the current working parameter; The operating state of the gas turbine is adjusted based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

2. The method according to claim 1, characterized in that The step of adjusting the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range includes: generating a target adjustment order of each working parameter to be adjusted based on the adjustment priority and the working parameter to be adjusted; The operating state of the gas turbine is adjusted according to the target adjustment sequence and the target fuel adjustment strategy corresponding to each operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

3. The method according to claim 2, characterized in that The working parameters to be adjusted include: NOx exhaust concentration, CO exhaust concentration and combustion chamber pressure pulsation parameters of the gas turbine in various frequency bands; The operating state of the gas turbine is adjusted according to the target fuel adjustment strategy corresponding to each operating parameter to be adjusted, including: When the operating parameter to be adjusted is NOx exhaust concentration, at least one of the following steps is performed: controlling the gas turbine to perform flue gas circulation; Increasing the valve opening corresponding to the air in the gas turbine; The combustion temperature of each zone of the combustion chamber in the gas turbine is controlled.

4. The method according to claim 3, characterized in that The combustion control method of the gas turbine further includes: When the working parameter to be adjusted is CO exhaust concentration, at least one of the following steps is performed: Open the premixing chamber so that the fuel and air are mixed in the premixing chamber before entering the combustion chamber; adjusting the pressure pulsation parameters of the combustion chamber; The valve opening of at least one fuel inlet communicating with the combustion chamber is controlled to control the fuel flow rate.

5. The method according to claim 4, characterized in that The combustion control method of the gas turbine further includes: When the working parameter to be adjusted is a combustion chamber pressure pulsation parameter, continuously acquiring the pressure pulsation parameter in the combustion chamber; Performing data analysis on the pressure pulsation parameters to determine the load state of the combustion chamber; A valve opening of at least one fuel inlet communicating with the combustion chamber is adjusted based on the load state.

6. The method according to claim 5, characterized in that The step of adjusting the valve opening of at least one fuel inlet connected to the combustion chamber based on the load state comprises: When the load state is a high load state, reducing the valve opening of at least one fuel inlet connected to the combustion chamber; When the load state is a low load state, the valve opening of at least one fuel inlet communicating with the combustion chamber is increased.

7. The method according to claim 3, characterized in that The priorities of the pressure pulsation parameter, the NOx exhaust concentration, and the CO exhaust concentration decrease in sequence.

8. A combustion control device for a gas turbine, characterized in that: The combustion control device of the gas turbine comprises: An acquisition module, used for acquiring current operating parameters of the gas turbine; A determination module, used to determine the working parameter to be adjusted and the adjustment priority between the working parameters to be adjusted according to the current working parameter; An adjustment module is used to adjust the operating state of the gas turbine based on the adjustment priority and the operating parameter to be adjusted until the operating parameter to be adjusted is reduced to within a preset safe operating parameter range.

9. A combustion control device for a gas turbine, characterized in that: The combustion control device of the gas turbine includes: a memory, a processor, and a combustion control program of the gas turbine stored in the memory and executable on the processor, wherein the combustion control program of the gas turbine is configured to implement the steps of the combustion control method of the gas turbine according to any one of claims 1 to 7.

10. A storage medium, characterized in that: The storage medium stores a combustion control program of a gas turbine, and when the combustion control program of the gas turbine is executed by a processor, the steps of the combustion control method of the gas turbine according to any one of claims 1 to 7 are implemented.

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